CN115056972A - Liftable rotor wing fairing of composite wing aircraft - Google Patents

Abstract

The invention discloses a liftable rotor wing fairing of a composite wing aircraft, which comprises a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft; the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove; the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head liftable fairing and the tail liftable fairing are respectively positioned above the two rotors, and according to different flight modes of the composite wing aircraft, the head liftable fairing and the tail liftable fairing are controlled to descend and are matched with the first groove and the second groove, so that the flight resistance of the composite wing aircraft is reduced, the pneumatic efficiency of the composite wing aircraft is improved, the voyage and the time of voyage are increased, and the flight stability is improved.

Description

Liftable rotor wing fairing of composite wing aircraft

Technical Field

The invention relates to the technical field of composite wing aircrafts, in particular to a liftable rotor wing fairing of a composite wing aircraft.

Background

The composite wing aircraft is an aircraft combining the advantages of a fixed wing aircraft and a multi-rotor aircraft, and has the advantages of both the fixed wing aircraft and the multi-rotor aircraft. The aircraft can take off and land vertically without a runway, and is switched to a fixed wing high-speed flight mode after taking off, so that the energy consumption is reduced, the aircraft has the characteristics of flexibility and adaptability to complex environments, and has wide application prospects in the aspects of emergency rescue, aerial surveying and mapping, natural resource monitoring and the like.

The composite wing aircraft is divided into three working modes, namely a multi-rotor mode, a multi-rotor fixed wing transition mode and a fixed wing mode. Wherein, many rotors mode is used for unmanned aerial vehicle's take off and land and hover, and the fixed wing mode is used for unmanned aerial vehicle's level to fly and cruises, and under this mode, the rotor is out of work, and many rotors fixed wing transition mode mainly used is many rotors mode and the mode transition between the fixed wing mode switches. For the unmanned aerial vehicle in long voyage, the operation time of the horizontal flight mode is more than 90%.

The existing composite wing aircraft has irregular shapes of wing support arms, motors and rotors, and is usually arranged in the middle of wings, and the wing support arms, the motors and the rotors of the composite wing aircraft increase flight resistance in a horizontal flight mode, thereby shortening the flight distance and the flight time of the composite wing aircraft.

Disclosure of Invention

Aiming at the problems in the prior art, the invention aims to provide a liftable rotor wing fairing of a composite wing aircraft, which solves the problems that the flight distance and the flight time of the composite wing aircraft are shortened due to increased flight resistance of a wing support arm, a motor and a rotor wing in the horizontal flight mode of the existing composite wing aircraft.

In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:

the utility model provides a liftable rotor wing fairing of a composite wing aircraft, which comprises a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft;

the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove;

the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head part liftable fairing and the tail part liftable fairing are respectively positioned above the two rotor wings.

The shapes of the fixed fairing, the head part liftable fairing and the tail part liftable fairing are all streamline, and the shapes of the head part liftable fairing and the tail part liftable fairing are in smooth transition with the shapes of the head part and the tail part of the fixed fairing.

The basic principle of the scheme is as follows: the composite wing aircraft comprises a support arm, wherein two ends of the support arm are respectively provided with a rotor and a rotor motor used for driving the rotor to rotate, the support arm and the rotor motor are arranged in a fixed fairing, the rotors are respectively positioned at the top of a first groove and a second groove, and the purpose is to ensure that the spatial position of the fixed fairing does not influence the rotation of the rotor of the composite wing aircraft.

When the composite wing aircraft is about to take off or is switched from a fixed wing mode to a rotor wing mode, the head liftable fairing and the tail liftable fairing ascend to specified positions, so that the spatial positions of the head liftable fairing and the tail liftable fairing do not influence the rotation of the rotor wing, and the rotor wing of the composite wing aircraft rotates to complete the mode switching work; when the composite wing aircraft will descend or switch to the fixed wing mode from the rotor mode, treat rotor stall back, head liftable fairing and afterbody liftable fairing descend to with the top cooperation back of first recess and second recess, the appearance of fixed fairing is streamlined, can reduce composite wing aircraft's flight resistance, promote composite wing aircraft range and time of navigating, and head liftable fairing and afterbody liftable fairing can cover rotor and rotor motor, realize the protect function to rotor and rotor motor.

Further, two wings of the composite wing aircraft are respectively arranged on two sides of the fixed fairing.

Furthermore, as a specific setting mode of ascending and descending of the head part liftable fairing and the tail part liftable fairing, the lower end faces of the head part liftable fairing and the tail part liftable fairing are both provided with electric push rods, the extending ends of the electric push rods are fixedly connected with the lower end face of the head part liftable fairing or the tail part liftable fairing, and the tail end of each electric push rod is fixedly connected with the inside of the fixed fairing.

Furthermore, the lower terminal surface of head liftable radome fairing and afterbody liftable radome fairing is matched with two electric putter, and the interval between two electric putter is greater than the diameter of rotation of rotor, avoids electric putter's setting to interfere the rotary motion of rotor.

The invention has the beneficial effects that: 1. the lifting rotor wing fairing of the composite wing aircraft in the scheme has the advantages that the fixed fairing, the head lifting fairing and the tail lifting fairing are streamline in appearance, airflow separation of wings near the support arm of the composite wing aircraft can be obviously weakened, airflow smoothly flows through the whole fairing and the surfaces of the wings, the pneumatic efficiency of the composite wing aircraft is improved, the voyage and the time of voyage are increased, and the flying stability is improved.

2. The lifting and descending of the head lifting fairing and the tail lifting fairing are realized through the vertical movement of the extending end of the electric push rod, the lifting process of the head lifting fairing and the tail lifting fairing is carried out after the composite wing aircraft enters a stable level flight state, the electric push rod and the rotor motor are not required to be synchronously controlled, and the control problem caused by mode switching does not exist. In addition, the lift force of the composite wing aircraft in the flat flight process can not be reduced in the descending process of the head liftable fairing and the tail liftable fairing, and extra flight control instructions and power can not be called to stabilize the posture of the composite wing aircraft.

3. When the composite wing aircraft is in a horizontal flight mode, the rotor and the rotor motor can be covered by the whole fairing in space, the composite wing aircraft can collide with birds, buildings and trees when flying at a high speed, the damage to the rotor and the rotor motor can be reduced by the fairing, and the protection functions of the two structures are realized. The head part liftable fairing and the tail part liftable fairing cover the upper portion of the rotor wing, and the head part liftable fairing and the tail part liftable fairing can play a role of rain sheltering in rainy days, so that the rotor wing motor is prevented from being out of work due to the fact that a large amount of rainwater is immersed into the rotor wing motor.

Drawings

Fig. 1 is a schematic view of the external structure of a liftable rotor fairing of a composite wing aircraft.

Fig. 2 is a schematic structural view of a liftable rotor fairing of the composite wing aircraft after the liftable fairing at the head part and the liftable fairing at the tail part are lifted.

Fig. 3 is a schematic view of the internal structure of a liftable rotor fairing of a compound wing aircraft.

Fig. 4 is a schematic structural view of a conventional composite wing aircraft without a fairing.

Wherein, 1, fixing a fairing; 2. a first groove; 3. a second groove; 4. the head part can lift the fairing; 5. the tail part can lift the fairing; 6. an electric push rod; 7. a rotor; 8. a rotor motor; 9. a support arm; 10. an airfoil.

Detailed Description

The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.

As shown in fig. 1 to 4, the invention provides a liftable rotor fairing of a composite wing aircraft, which comprises a fixedfairing 1, wherein the fixedfairing 1 is used for wrapping the composite wing aircraft.

The composite wing aircraft comprises asupport arm 9 andwings 10, wherein two ends of thesupport arm 9 are respectively provided with arotor 7 and arotor motor 8 for driving therotor 7 to rotate, thesupport arm 9 and therotor motor 8 are arranged inside the fixedfairing 1, and the twowings 10 of the composite wing aircraft are respectively arranged on two sides of the fixedfairing 1.

The head and the tail of the fixedfairing 1 are respectively provided with afirst groove 2 and asecond groove 3, and tworotors 7 of the composite wing aircraft are respectively positioned at the tops of thefirst groove 2 and thesecond groove 3.

The head part of the fixedfairing 1 is provided with a head partliftable fairing 4 matched with thefirst groove 2, and the tail part of the fixedfairing 1 is provided with a tail partliftable fairing 5 matched with thesecond groove 3; thehead lifting fairing 4 and the tail liftingfairing 5 are respectively positioned above the tworotor wings 7. When the compound wing aircraft was in the horizontal flight mode, whole radome fairing can coverrotor 7 androtor motor 8 in the space, and compound wing aircraft probably takes place the striking with bird, building, tree when high-speed flight, and the radome fairing can reduce the injury thatrotor 7 androtor motor 8 received, realizes the protect function to these two structures.

Simultaneously, headliftable fairing 4 and afterbodyliftable fairing 5 cover inrotor 7 top, and in the rainy day, headliftable fairing 4 and afterbodyliftable fairing 5 can play the effect of taking shelter from the rain, avoid a large amount of rainwater to diprotor motor 8 and causerotor motor 8 to become invalid.

The lower terminal surface of headliftable fairing 4 and afterbodyliftable fairing 5 all is provided with twoelectric putter 6, and the interval between twoelectric putter 6 is greater than the diameter of rotation ofrotor 7, avoidselectric putter 6's setting to interfere the rotary motion ofrotor 7, and the end that stretches out of everyelectric putter 6 and the lower terminal surface fixed connection of headliftable fairing 4 or afterbodyliftable fairing 5, the tail end ofelectric putter 6 and the inside fixed connection of fixedfairing 1. The lifting and descending of thehead lifting fairing 4 and the tail liftingfairing 5 are realized by controlling the vertical movement of the extending end of theelectric push rod 6. The lifting process of thehead lifting fairing 4 and thetail lifting fairing 5 is carried out after the composite wing aircraft enters a stable flat flying state, the control of theelectric push rod 6 and therotor motor 8 does not need to be carried out synchronously, and the control problem caused by mode switching does not exist. In addition, in the descending process of the head partliftable fairing 4 and the tail partliftable fairing 5, the lifting force of the composite wing aircraft in the flat flight process cannot be reduced, and extra flight control instructions and power cannot be called to stabilize the posture of the composite wing aircraft.

When the composite wing aircraft is about to take off or is switched from a fixed wing mode to a rotor wing mode, theelectric push rod 6 drives the headliftable fairing 4 and the tailliftable fairing 5 to rise to the designated positions, so that the spatial positions of the head liftable fairing and the tail liftable fairing do not influence the rotation of therotor wing 7, and therotor wing 7 of the composite wing aircraft rotates to complete the mode switching work; when the compound wing aircraft will descend or switch to the fixed wing mode from the rotor mode, treatrotor 7 stall back,electric putter 6 drives headliftable fairing 4 and afterbodyliftable fairing 5 and descends to withfirst recess 2 andsecond recess 3's top cooperation back, form a holistic fairing, compound wing aircraft'ssupport arm 9,rotor motor 8 androtor 7 are all wrapped up in holistic fairing, can reduce compound wing aircraft's flight resistance, promote compound wing aircraft range and when navigating, and headliftable fairing 4 and afterbodyliftable fairing 5 can coverrotor 7 androtor motor 8, realize the protect function torotor 7 androtor motor 8.

Preferably, but not limited to, the shapes of the fixedfairing 1, the headliftable fairing 4 and the tailliftable fairing 5 are streamline, the shapes of the headliftable fairing 4 and the tailliftable fairing 5 and the shapes of the head and the tail of the fixedfairing 1 are in smooth transition, the airflow separation of thewings 10 near thesupport arm 9 of the composite wing aircraft can be obviously weakened, the airflow smoothly flows through the whole fairing and the surfaces of thewings 10, the aerodynamic efficiency of the composite wing aircraft is improved, and the flight range and the flight time are increased, so that the flight stability is improved.

Claims (5)

1. A liftable rotor wing fairing of a composite wing aircraft is characterized by comprising a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft;

the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove;

the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head part liftable fairing and the tail part liftable fairing are respectively positioned above the two rotor wings.

2. The liftable rotor fairing of a composite wing aircraft according to claim 1, wherein two wings of the composite wing aircraft are respectively disposed on both sides of the fixed fairing.

3. The liftable rotor wing fairing of the composite wing aircraft according to claim 1, wherein the lower end surfaces of the head liftable fairing and the tail liftable fairing are respectively provided with an electric push rod, the extending end of the electric push rod is fixedly connected with the lower end surface of the head liftable fairing or the tail liftable fairing, and the tail end of the electric push rod is fixedly connected with the inside of the fixed fairing.

4. The liftable rotor fairing of the composite wing aircraft according to claim 3, wherein the lower end surfaces of the head liftable fairing and the tail liftable fairing are matched with two electric push rods, and the distance between the two electric push rods is larger than the rotation diameter of the rotor.

5. The liftable rotor fairing of a composite wing aircraft according to claim 1, wherein the shapes of the fixed fairing, the head liftable fairing and the tail liftable fairing are streamline, and the shapes of the head liftable fairing and the tail liftable fairing are in smooth transition with the shapes of the head part and the tail part of the fixed fairing.

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